EP2075416A1 - Method for manufacturing a turboshaft engine element and device obtained using same - Google Patents

Method for manufacturing a turboshaft engine element and device obtained using same Download PDF

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Publication number
EP2075416A1
EP2075416A1 EP07150429A EP07150429A EP2075416A1 EP 2075416 A1 EP2075416 A1 EP 2075416A1 EP 07150429 A EP07150429 A EP 07150429A EP 07150429 A EP07150429 A EP 07150429A EP 2075416 A1 EP2075416 A1 EP 2075416A1
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EP
European Patent Office
Prior art keywords
abradable material
track
turbomachine
shell
outer shell
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP07150429A
Other languages
German (de)
French (fr)
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EP2075416B1 (en
Inventor
Alain Derclaye
Rodolphe Lebrun
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aero Boosters SA
Original Assignee
Techspace Aero SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP07150429A priority Critical patent/EP2075416B1/en
Priority to CA2648862A priority patent/CA2648862C/en
Priority to US12/343,675 priority patent/US8192150B2/en
Priority to BRPI0805624-2A priority patent/BRPI0805624A2/en
Priority to JP2008332353A priority patent/JP5575392B2/en
Priority to RU2008151973/06A priority patent/RU2485326C2/en
Priority to CN2008101891578A priority patent/CN101497976B/en
Priority to MX2009000257A priority patent/MX2009000257A/en
Publication of EP2075416A1 publication Critical patent/EP2075416A1/en
Application granted granted Critical
Publication of EP2075416B1 publication Critical patent/EP2075416B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C39/00—Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor
    • B29C39/02—Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor for making articles of definite length, i.e. discrete articles
    • B29C39/10—Shaping by casting, i.e. introducing the moulding material into a mould or between confining surfaces without significant moulding pressure; Apparatus therefor for making articles of definite length, i.e. discrete articles incorporating preformed parts or layers, e.g. casting around inserts or for coating articles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C67/00—Shaping techniques not covered by groups B29C39/00 - B29C65/00, B29C70/00 or B29C73/00
    • B29C67/24—Shaping techniques not covered by groups B29C39/00 - B29C65/00, B29C70/00 or B29C73/00 characterised by the choice of material
    • B29C67/246—Moulding high reactive monomers or prepolymers, e.g. by reaction injection moulding [RIM], liquid injection moulding [LIM]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
    • B29K2083/00—Use of polymers having silicon, with or without sulfur, nitrogen, oxygen, or carbon only, in the main chain, as moulding material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49323—Assembling fluid flow directing devices, e.g., stators, diaphragms, nozzles
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making

Definitions

  • the invention relates to a method for manufacturing a turbomachine element and more particularly to a subassembly comprising an outer shell carrying a stator vane stage and an annular track of abradable material opposite which the ends of the moving blades of a rotor stage.
  • the invention relates more particularly to an improvement making it possible at the same time to simplify the formation of the track of abradable material and to reduce the axial space requirement and the weight of the element as a whole.
  • a turbomachine stage such as for example a compression stage in a compressor is arranged between an outer shell and an inner shell, coaxial.
  • the stationary stator vanes extend between the two ferrules.
  • the blades are rotated inside the outer shell so that the ends of these vanes move opposite a track of abradable material deposited on the inner surface of the outer ring, upstream of the stator vanes.
  • upstream and downstream make it possible to locate the structural elements relative to one another by taking as a reference the direction of flow of the fluid in the vein, that is to say inside the outer shell.
  • the figure 1 represents a known subassembly constituted by the outer shell 11, the stator vanes 13 and the track of abradable material 15.
  • the outer shell 11 has an internal rib 17 which separates an upstream portion 19 where is the track of abradable material 15 of a downstream portion 21 which are mounted on the stator vanes 13.
  • Each blade has a platform 23 embedded in an annular groove 25 of the outer ring.
  • the rib 17 forms the upstream edge of this groove.
  • the blades 13 are fixed fixed to the outer shell 11 by bolts 27.
  • the final shape of the outer ring, the inner side, is generally obtained by machining.
  • the ferrule is generally metallic, for example aluminum alloy, titanium or steel.
  • the abradable material is often a mixture of aluminum and hot-deposited (plasma) or cold resin, or an "RTV" silicone.
  • One of the objectives of the invention is to simplify the outer shell 11 and in particular to remove the rib 17.
  • the basic idea of the invention is to use the platforms of the stator vanes to form part of the confinement means for placing the abradable material on the inner face of the ferrule.
  • the invention relates to a method of manufacturing a turbomachine element comprising an outer shell comprising a first portion internally provided with a track of abradable material and a second part to which are fixed stator blade platforms, characterized in that the stator vanes are assembled to the ferrule so as to define a substantially continuous annular field and in that the abradable material is deposited within said first part by using this field to delimit an edge of said track of abradable material.
  • said first part is upstream and said second part is downstream.
  • the invention also makes it possible to manufacture the outer shell made of a composite material based on carbon or glass fibers because it is possible to obtain a substantially constant fog thickness over most of the length of the shell.
  • the abradable material is injected in finished dimensions. This type of injection is known per se and avoids any subsequent machining.
  • the abradable material is a silicone-based compound.
  • the material may be in contact with the edges of the platforms of the stator vanes. It is not necessary to provide a clearance between the track of abradable material and the platforms. On the contrary, the vibrations can be damped by the silicone.
  • the invention does not exclude depositing another type of abradable material (hot plasma deposition) or an unfinished silicone-based injected material.
  • the invention also relates to a turbomachine element obtained by implementing the method and comprising an outer shell comprising an upstream portion internally provided with a track of abradable material and a downstream part to which are attached stator blade platforms, characterized in that the downstream edge of said track of abradable material is adjacent to all the upstream edges of said stator blade platforms.
  • the outer shell may advantageously be made of a composite material based on carbon fibers or glass.
  • the invention also relates to any turbomachine comprising at least one element according to the above definition. It applies in particular to a low-pressure compressor of a turbojet engine.
  • the turbomachine element represented on the figure 2 is part of a compression stage of a compressor. It consists of an outer shell 11 comprising an upstream portion 19 internally provided with a track of abradable material 15 and a downstream portion 21 to which stator vanes 13 are attached.
  • the platforms 23 of the stator vanes are positioned by one-sided contact within the shell 11, along a single downstream positioning field 31. Indeed, the midrib is removed. Positioning is therefore easier.
  • the stator vanes 13 are mounted side by side through bolts 27. They thus define a substantially continuous annular field 33, upstream. The presence of this field is used to deposit the abradable material on the inner face of the upstream portion 19 of the ferrule by using this field to define the downstream edge of the track of abradable material 15.
  • the annular field 33 formed by the platforms 23 constitutes an end wall of a mold 37 for injecting the abradable material.
  • the abradable material is a silicone compound.
  • the injection of the silicone is done with finished dimensions so that no further machining is necessary.
  • the withdrawal of the mold 37 after injection of the abradable material results in the configuration of the figure 3 .
  • the turbomachine element is finished and can enter into the constitution of the compressor, the rotor blades integral with a rotor (not shown) coming opposite the track of abradable material 15.
  • the outer shell 11 whose shape is much simpler, with a substantially constant wall thickness over most of its length, can easily be made of non-metallic material, for example material composite made of carbon fiber or glass.
  • non-metallic material for example material composite made of carbon fiber or glass.
  • abradable material based on silicone improves vibration damping of the platforms.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The method involves assembling stator vanes (13) at an external shell (11), such that platforms (23) of the vanes define a continuous annular field (33) inside the shell. An abradable material e.g. silicone based compound, is placed inside an upstream part (19) of the shell by using the field for delimiting an edge of an abradable material path (15), where the upstream part is provided inside the path. The platforms of the stator vanes are fixed to a downstream part (21) of the shell. The shell is made of glass or carbon fiber based composite material. An independent claim is also included for a turbomachine element comprising an external shell.

Description

L'invention se rapporte à un procédé de fabrication d'un élément de turbomachine et plus particulièrement un sous-ensemble comprenant une virole extérieure portant un étage d'aubes statoriques et une piste annulaire de matériau abradable en regard de laquelle se déplacent les extrémités des aubes mobiles d'un étage de rotor. L'invention concerne plus particulièrement un perfectionnement permettant tout à la fois de simplifier la formation de la piste de matériau abradable et de réduire l'encombrement axial et le poids de l'élément, dans son ensemble.The invention relates to a method for manufacturing a turbomachine element and more particularly to a subassembly comprising an outer shell carrying a stator vane stage and an annular track of abradable material opposite which the ends of the moving blades of a rotor stage. The invention relates more particularly to an improvement making it possible at the same time to simplify the formation of the track of abradable material and to reduce the axial space requirement and the weight of the element as a whole.

Un étage de turbomachine, comme par exemple un étage de compression dans un compresseur est agencé entre une virole extérieure et une virole intérieure, coaxiales. Les aubes fixes statoriques s'étendent entre les deux viroles. Les aubes mobiles sont entraînées en rotation à l'intérieur de la virole extérieure en sorte que les extrémités de ces aubes se déplacent en regard d'une piste de matériau abradable déposé sur la surface interne de la virole extérieure, en amont des aubes statoriques.A turbomachine stage, such as for example a compression stage in a compressor is arranged between an outer shell and an inner shell, coaxial. The stationary stator vanes extend between the two ferrules. The blades are rotated inside the outer shell so that the ends of these vanes move opposite a track of abradable material deposited on the inner surface of the outer ring, upstream of the stator vanes.

Dans la suite de la description les termes "amont" et "aval" permettent de situer les éléments de structure les uns par rapport aux autres en prenant pour référence le sens d'écoulement du fluide dans la veine, c'est-à-dire à l'intérieur de la virole extérieure.In the remainder of the description, the terms "upstream" and "downstream" make it possible to locate the structural elements relative to one another by taking as a reference the direction of flow of the fluid in the vein, that is to say inside the outer shell.

La figure 1 représente un sous-ensemble connu constitué par la virole extérieure 11, les aubes statoriques 13 et la piste de matériau abradable 15. Selon cet agencement, la virole extérieure 11 présente une nervure interne 17 qui sépare une partie amont 19 où se trouve la piste de matériau abradable 15 d'une partie aval 21 où sont montées les aubes statoriques 13. Chaque aube présente une plateforme 23 encastrée dans une gorge annulaire 25 de la virole extérieure. La nervure 17 forme le bord amont de cette gorge. Dans l'exemple décrit, les aubes 13 fixes sont assemblées à la virole extérieure 11 par des boulons 27. La forme finale de la virole extérieure, du côté interne, est généralement obtenue par usinage. La virole est généralement métallique, par exemple en alliage d'aluminium, de titane ou d'acier. Le matériau abradable est souvent un mélange d'aluminium et de résine déposé à chaud (plasma) ou à froid, ou un silicone "RTV".The figure 1 represents a known subassembly constituted by the outer shell 11, the stator vanes 13 and the track of abradable material 15. According to this arrangement, the outer shell 11 has an internal rib 17 which separates an upstream portion 19 where is the track of abradable material 15 of a downstream portion 21 which are mounted on the stator vanes 13. Each blade has a platform 23 embedded in an annular groove 25 of the outer ring. The rib 17 forms the upstream edge of this groove. In the example described, the blades 13 are fixed fixed to the outer shell 11 by bolts 27. The final shape of the outer ring, the inner side, is generally obtained by machining. The ferrule is generally metallic, for example aluminum alloy, titanium or steel. The abradable material is often a mixture of aluminum and hot-deposited (plasma) or cold resin, or an "RTV" silicone.

L'un des objectifs de l'invention est de simplifier la virole extérieure 11 et notamment de supprimer la nervure 17.One of the objectives of the invention is to simplify the outer shell 11 and in particular to remove the rib 17.

L'idée de base de l'invention consiste à utiliser les plateformes des aubes statoriques pour constituer une partie des moyens de confinement permettant la mise en place du matériau abradable sur la face interne de la virole.The basic idea of the invention is to use the platforms of the stator vanes to form part of the confinement means for placing the abradable material on the inner face of the ferrule.

Plus particulièrement, l'invention concerne un procédé de fabrication d'un élément de turbomachine comportant une virole extérieure comprenant une première partie pourvue intérieurement d'une piste de matériau abradable et une seconde partie à laquelle sont fixées des plateformes d'aubes statoriques, caractérisé en ce qu'on assemble les aubes statoriques à la virole de façon à définir un champ annulaire sensiblement continu et en ce qu'on dépose le matériau abradable à l'intérieur de ladite première partie en utilisant ce champ pour délimiter un bord de ladite piste de matériau abradable.More particularly, the invention relates to a method of manufacturing a turbomachine element comprising an outer shell comprising a first portion internally provided with a track of abradable material and a second part to which are fixed stator blade platforms, characterized in that the stator vanes are assembled to the ferrule so as to define a substantially continuous annular field and in that the abradable material is deposited within said first part by using this field to delimit an edge of said track of abradable material.

Dans l'exemple, ladite première partie est à l'amont et ladite seconde partie est à l'aval.In the example, said first part is upstream and said second part is downstream.

On peut ainsi diminuer la longueur de la virole extérieure puisque la nervure 17 est supprimée. L'invention permet aussi de fabriquer la virole extérieure en matériau composite à base de fibres de carbone ou de verre car on peut obtenir une épaisseur de voile pratiquement constante sur la plus grande partie de la longueur de la virole.It is thus possible to reduce the length of the outer shell since the rib 17 is removed. The invention also makes it possible to manufacture the outer shell made of a composite material based on carbon or glass fibers because it is possible to obtain a substantially constant fog thickness over most of the length of the shell.

Selon une caractéristique avantageuse, le matériau abradable est injecté à cotes finies. Ce type d'injection est connu en soi et permet d'éviter tout usinage ultérieur.According to an advantageous characteristic, the abradable material is injected in finished dimensions. This type of injection is known per se and avoids any subsequent machining.

Par exemple, le matériau abradable est un composé à base de silicone. Dans ces conditions, le matériau peut être en contact avec les bords des plateformes des aubes statoriques. Il n'est pas nécessaire de prévoir un jeu entre la piste de matériau abradable et les plateformes. Au contraire, les vibrations peuvent être amorties par le silicone.For example, the abradable material is a silicone-based compound. Under these conditions, the material may be in contact with the edges of the platforms of the stator vanes. It is not necessary to provide a clearance between the track of abradable material and the platforms. On the contrary, the vibrations can be damped by the silicone.

Bien entendu, l'invention n'exclut pas de déposer un autre type de matériau abradable (déposition par plasma à chaud) voire un matériau à base de silicone injecté à cotes non finies.Of course, the invention does not exclude depositing another type of abradable material (hot plasma deposition) or an unfinished silicone-based injected material.

L'invention concerne également un élément de turbomachine obtenu par mise en oeuvre du procédé et comportant une virole extérieure comprenant une partie amont pourvue intérieurement d'une piste de matériau abradable et une partie aval à laquelle sont fixées des plateformes d'aubes statoriques, caractérisé en ce que le bord aval de ladite piste de matériau abradable jouxte l'ensemble des bords amont desdites plateformes d'aubes statoriques.The invention also relates to a turbomachine element obtained by implementing the method and comprising an outer shell comprising an upstream portion internally provided with a track of abradable material and a downstream part to which are attached stator blade platforms, characterized in that the downstream edge of said track of abradable material is adjacent to all the upstream edges of said stator blade platforms.

Comme mentionné précédemment, la virole extérieure peut avantageusement être en matériau composite à base de fibres de carbone ou de verre.As mentioned above, the outer shell may advantageously be made of a composite material based on carbon fibers or glass.

L'invention vise également toute turbomachine comprenant au moins un élément selon la définition qui précède. Elle s'applique notamment à un compresseur basse pression d'un turboréacteur.The invention also relates to any turbomachine comprising at least one element according to the above definition. It applies in particular to a low-pressure compressor of a turbojet engine.

L'invention sera mieux comprise et d'autres avantages de celle-ci apparaîtront plus clairement à la lumière de la description qui va suivre donnée uniquement à titre d'exemples et faite en référence aux dessins annexés, dans lesquels :

  • la figure 1 est une vue en coupe axiale partielle d'un élément de turbomachine selon l'état de la technique ;
  • la figure 2 illustre un élément de turbomachine semblable, conforme à l'invention et montre plus particulièrement une phase du procédé conforme à l'invention ; et
  • la figure 3 est une vue analogue à la figure 2 illustrant l'élément de turbomachine terminé.
The invention will be better understood and other advantages thereof will appear more clearly in the light of the following description given solely by way of example and with reference to the accompanying drawings, in which:
  • the figure 1 is a partial axial sectional view of a turbomachine element according to the state of the art;
  • the figure 2 illustrates a similar turbomachine element according to the invention and more particularly shows a phase of the process according to the invention; and
  • the figure 3 is a view similar to the figure 2 illustrating the completed turbomachine element.

L'élément de turbomachine représenté sur la figure 2 constitue une partie d'un étage de compression d'un compresseur. Il se compose d'une virole extérieure 11 comprenant une partie amont 19 pourvue intérieurement d'une piste de matériau abradable 15 et une partie aval 21 à laquelle sont fixées des aubes statoriques 13.The turbomachine element represented on the figure 2 is part of a compression stage of a compressor. It consists of an outer shell 11 comprising an upstream portion 19 internally provided with a track of abradable material 15 and a downstream portion 21 to which stator vanes 13 are attached.

Contrairement au dispositif connu de la figure 1, les plateformes 23 des aubes statoriques sont positionnées par contact d'un seul côté à l'intérieur de la virole 11, le long d'un seul champ aval de positionnement 31. En effet, la nervure médiane est supprimée. Le positionnement est donc plus facile. Les aubes statoriques 13 sont montées côte à côté grâce à des boulons 27. Elles définissent ainsi un champ annulaire 33 sensiblement continu, à l'amont. La présence de ce champ est mise à profit pour déposer le matériau abradable à la face interne de la partie amont 19 de la virole en utilisant ce champ pour délimiter le bord aval de la piste de matériau abradable 15. C'est ce qui est illustré à la figure 2 où l'on voit que le champ annulaire 33 formé par les plateformes 23 constitue une paroi terminale d'un moule 37 permettant d'injecter le matériau abradable. Dans cet exemple, le matériau abradable est un composé à base de silicone. L'injection du silicone se fait à cotes finies en sorte qu'aucun usinage ultérieur n'est nécessaire. Le retrait du moule 37 après injection du matériau abradable aboutit à la configuration de la figure 3. L'élément de turbomachine est terminé et peut entrer dans la constitution du compresseur, les aubes mobiles solidaires d'un rotor (non représentées) venant en regard de la piste de matériau abradable 15.Unlike the known device of the figure 1 the platforms 23 of the stator vanes are positioned by one-sided contact within the shell 11, along a single downstream positioning field 31. Indeed, the midrib is removed. Positioning is therefore easier. The stator vanes 13 are mounted side by side through bolts 27. They thus define a substantially continuous annular field 33, upstream. The presence of this field is used to deposit the abradable material on the inner face of the upstream portion 19 of the ferrule by using this field to define the downstream edge of the track of abradable material 15. This is illustrated to the figure 2 where we see that the annular field 33 formed by the platforms 23 constitutes an end wall of a mold 37 for injecting the abradable material. In this example, the abradable material is a silicone compound. The injection of the silicone is done with finished dimensions so that no further machining is necessary. The withdrawal of the mold 37 after injection of the abradable material results in the configuration of the figure 3 . The turbomachine element is finished and can enter into the constitution of the compressor, the rotor blades integral with a rotor (not shown) coming opposite the track of abradable material 15.

De plus, comme indiqué ci-dessus, la virole extérieure 11 dont la forme est beaucoup plus simple, avec une épaisseur de paroi pratiquement constante sur la plus grande partie de sa longueur, peut facilement être réalisée en matériau non métallique, par exemple en matériau composite à base de fibres de carbone ou de verre. L'utilisation d'un matériau abradable à base de silicone améliore l'amortissement vibratoire des plateformes.In addition, as indicated above, the outer shell 11 whose shape is much simpler, with a substantially constant wall thickness over most of its length, can easily be made of non-metallic material, for example material composite made of carbon fiber or glass. The use of an abradable material based on silicone improves vibration damping of the platforms.

Le procédé défini ci-dessus peut aussi s'appliquer même si l'abradable est déposé "à cotes non finies", ce qui implique un usinage de finition.The process defined above can also be applied even if the abradable is deposited "unfinished odds", which implies finishing machining.

Il est aussi possible de mettre en oeuvre le procédé avec l'application d'un abradable par plasma, ce qui aboutit généralement à un dépôt d'abradable à cotes non finies.It is also possible to implement the method with the application of a plasma abradable, which generally results in an unfinished dimension abradable deposit.

Claims (10)

Procédé de fabrication d'un élément de turbomachine comportant une virole extérieure (11) comprenant une première partie (19) pourvue intérieurement d'une piste de matériau abradable (15) et une seconde partie (21) à laquelle sont fixées des plateformes d'aubes statorique, caractérisé en ce qu'on assemble les aubes statoriques à la virole de façon à définir un champ annulaire (33) sensiblement continu et en ce qu'on dépose le matériau abradable à l'intérieur de ladite première partie en utilisant ce champ pour délimiter un bord de ladite piste de matériau abradable.A method of manufacturing a turbomachine element having an outer shell (11) comprising a first portion (19) internally provided with a track of abradable material (15) and a second portion (21) to which are attached stator blade, characterized in that the stator vanes are connected to the ferrule so as to define a substantially continuous annular field (33) and in that the abradable material is deposited within said first part using this field to delimit an edge of said track of abradable material. Procédé selon la revendication 1, caractérisé en ce qu'on injecte ledit matériau abradable à cotes finies.Process according to claim 1, characterized in that said abradable material is injected with finished dimensions. Procédé selon la revendication 1, caractérisé en ce qu'on dépose ledit matériau abradable à cotes non finies, avec usinage ultérieur.Process according to claim 1, characterized in that said undefined abradable material is deposited with subsequent machining. Procédé selon la revendication 1 ou 2, caractérisé en ce que ledit matériau abradable est un composé à base de silicone.Process according to claim 1 or 2, characterized in that said abradable material is a silicone-based compound. Procédé sleon la revendication 1 ou 3, caractérisé en ce qu'on applique ledit abradable par projection plasma.Process according to Claim 1 or 3, characterized in that said abradable material is applied by plasma spraying. Elément de turbomachine comportant une virole extérieure (11) comprenant une partie amont (19) pourvue intérieurement d'une piste de matériau abradable (15) et une partie aval (21) à laquelle sont fixées des plateformes d'aubes statoriques, caractérisé en ce que le bord aval de ladite piste de matériau abradable jouxte l'ensemble des bords amont desdites plateformes d'aubes statoriques (23).Turbomachine element comprising an outer shell (11) comprising an upstream part (19) internally provided with a track of abradable material (15) and a downstream part (21) to which stator blade platforms are attached, characterized in that that the downstream edge of said track of abradable material is adjacent to all the upstream edges of said stator blade platforms (23). Elément de turbomachine selon la revendication 6, caractérisé en ce que ledit matériau abradable est un composé à base de silicone.Turbomachine element according to claim 6, characterized in that said abradable material is a silicone-based compound. Elément de turbomachine selon la revendication 7, caractérisé en ce que ledit matériau abradable est en contact avec l'ensemble des bords amont desdites plateformes (23).Turbomachine element according to claim 7, characterized in that said abradable material is in contact with all the upstream edges of said platforms (23). Elément de turbomachine selon l'une des revendications 6 à 8, caractérisé en ce que ladite virole extérieure (11) est en matériau composite à base de fibres de carbone ou de verre.Turbomachine element according to one of claims 6 to 8, characterized in that said outer shell (11) is made of composite material based on carbon fibers or glass. Turbomachine caractérisée en ce qu'elle comporte un élément selon l'une des revendications 6 à 9.Turbomachine characterized in that it comprises an element according to one of Claims 6 to 9.
EP07150429A 2007-12-27 2007-12-27 Method for manufacturing a turboshaft engine element and device obtained using same Active EP2075416B1 (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP07150429A EP2075416B1 (en) 2007-12-27 2007-12-27 Method for manufacturing a turboshaft engine element and device obtained using same
CA2648862A CA2648862C (en) 2007-12-27 2008-12-23 Method for manufacturing a turbomachine element and resulting device
US12/343,675 US8192150B2 (en) 2007-12-27 2008-12-24 Method of manufacturing a turbomachine element and device obtained in this way
JP2008332353A JP5575392B2 (en) 2007-12-27 2008-12-26 Method of manufacturing turbomachine element and apparatus obtained by the method
BRPI0805624-2A BRPI0805624A2 (en) 2007-12-27 2008-12-26 method for manufacturing a turbocharger element, and, turbocharger element
RU2008151973/06A RU2485326C2 (en) 2007-12-27 2008-12-26 Gas turbine engine element, method of its production and gas turbine engine with said element
CN2008101891578A CN101497976B (en) 2007-12-27 2008-12-29 Method for manufacturing a turbomachine element and resulting device
MX2009000257A MX2009000257A (en) 2007-12-27 2009-01-07 Method of manufacturing a turbomachine element and device obtained in this way .

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EP2075416B1 EP2075416B1 (en) 2011-05-18

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EP (1) EP2075416B1 (en)
JP (1) JP5575392B2 (en)
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CN107542499B (en) * 2017-09-30 2019-12-20 中国航发沈阳发动机研究所 Fan casing
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CN101497976B (en) 2013-06-19
BRPI0805624A2 (en) 2009-09-15
US8192150B2 (en) 2012-06-05
CA2648862C (en) 2015-12-01
MX2009000257A (en) 2009-06-26
RU2485326C2 (en) 2013-06-20
JP5575392B2 (en) 2014-08-20
CA2648862A1 (en) 2009-06-27
JP2009156263A (en) 2009-07-16
US20090175719A1 (en) 2009-07-09
EP2075416B1 (en) 2011-05-18
CN101497976A (en) 2009-08-05
RU2008151973A (en) 2010-07-10

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